Development of an Efficient M=0.80 Transonic Truss-Braced Wing Aircraft

Harrison, Neal A.; Gatlin, Gregory M.; Viken, Sally A.; Beyar, Michael; Dickey, Eric D.; Hoffman, Krishna; Reichenbach, Eric

doi:10.2514/6.2020-0011

Cited by 24 publications

(15 citation statements)

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“…This feature likely enables an improvement in performance over the high-speed design points where the cruise C L values are much lower, while aiding in reducing the overall wing loading for the high C L design point. Such a benefit suggests that lifting struts are aerodynamically favourable for transonic strut-braced wings, and may explain in part why Boeing has opted to incorporate and emphasie such a feature when transitioning from their Mach 0.70 design [8] to their Mach 0.745 [12] and Mach 0.80 variants [13]. It should be noted, however, that lifting struts can lead to structural design challenges associated with the impact of non-axial loads on buckling.…”

Section: Optimisation Resultsmentioning

confidence: 99%

“…Concerns over losses in airline productivity and compatibility with current air traffic management, however, have since motivated research into strut-and truss-braced wings at more conventional transonic speeds. For NASA and Boeing, this has culminated first in the development of a Mach 0.745 [12] variant, and then a variant for Mach 0.80 [13].…”

Section: Introductionmentioning

confidence: 99%

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Fuel burn evaluation of a transonic strut-braced-wing regional aircraft through multipoint aerodynamic optimisation

Chau

Zingg

2022

Aeronaut. j.

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This paper presents a relative fuel burn evaluation of the transonic strut-braced-wing configuration for the regional aircraft class in comparison to an equivalent conventional tube-and-wing aircraft. This is accomplished through multipoint aerodynamic shape optimisation based on the Reynolds-averaged Navier-Stokes equations. Aircraft concepts are first developed through low-order multidisciplinary design optimisation based on the design missions and top-level aircraft requirements of the Embraer E190-E2. High-fidelity aerodynamic shape shape optimisation is then applied to wing–body–tail models of each aircraft, with the objective of minimising the weighted-average cruise drag over a five-point operating envelope that includes the nominal design point, design points at $\pm 10\%$ nominal $C_L$ at Mach 0.78, and two high-speed cruise points at Mach 0.81. Design variables include angle-of-attack, wing (and strut) twist and section shape degrees of freedom, and horizontal tail incidence, while nonlinear constraints include constant lift, zero pitching moment, minimum wing and strut volume, and minimum maximum thickness-to-chord ratios. Results show that the multipoint optimised strut-braced wing maintains similar features to those of the single-point optimum, and compromises on-design performance by only two drag counts to achieve up to 11.6% reductions in drag at the off-design conditions. Introducing low-order estimates for approximating full aircraft performance, results indicate that the multipoint optimised strut-braced-wing regional jet offers a 13.1% improvement in cruise lift-to-drag ratio and a 7.8% reduction in block fuel over a 500nmi nominal mission when compared to the similarly optimised Embraer E190-E2-like conventional tube-and-wing aircraft.

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Section: Optimisation Resultsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Fuel burn evaluation of a transonic strut-braced-wing regional aircraft through multipoint aerodynamic optimisation

Chau

Zingg

2022

Aeronaut. j.

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“…An alternative version of the SBW is the truss-braced wing, where several additional structural members can be attached between the wing and the strut. The advantages of adding structural attachments are an increase in flutter speed, a decrease in overall wing weight and attractive fuel efficiency increases [59]. The SBW can potentially be optimised to decrease the energy demands through improved aerodynamic performance whilst maintaining the weight of a reference cantilever beam.…”

Section: Slender Wingsmentioning

confidence: 99%

Structural Power Performance Targets for Future Electric Aircraft

et al. 2021

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The development of commercial aviation is being driven by the need to improve efficiency and thereby lower emissions. All-electric aircraft present a route to eliminating direct fuel burning emissions, but their development is stifled by the limitations of current battery energy and power densities. Multifunctional structural power composites, which combine load-bearing and energy-storing functions, offer an alternative to higher-energy-density batteries and will potentially enable lighter and safer electric aircraft. This study investigated the feasibility of integrating structural power composites into future electric aircraft and assessed the impact on emissions. Using the Airbus A320 as a platform, three different electric aircraft configurations were designed conceptually, incorporating structural power composites, slender wings and distributed propulsion. The specific energy and power required for the structural power composites were estimated by determining the aircraft mission performance requirements and weight. Compared to a conventional A320, a parallel hybrid-electric A320 with structural power composites >200 Wh/kg could potentially increase fuel efficiency by 15% for a 1500 km mission. For an all-electric A320, structural power composites >400 Wh/kg could halve the specific energy or mass of batteries needed to power a 1000 km flight.

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“…Sustainable aviation fuels (SAF) include renewable biomass and waste resources with the potential to deliver the performance of petroleum-based jet fuel but with a fraction of its carbon footprint. Recent [6].…”

Section: Innovative Energy-efficient Aircraft Configurationsmentioning

confidence: 99%

“…While the original SUGAR TTBW aircraft concept flew at Mach 0.7, these studies have evolved to focus on a Mach = 0.80 design. Computational studies and wind tunnel test programs under SUGAR have shown a potential fuel burn reduction of ∼9% for a 3500nm mission as compared to a cantilever-wing design of equivalent technology [6]. The objective of the latest phases of the SUGAR program has therefore focused on further investigating and maturing the TTBW concept within the context of its potential applicability to modern commercial airliners.…”

Section: Transonic Truss-braced Wing (Ttbw)mentioning

confidence: 99%

Future aircraft concepts and design methods

McDonald¹,

German

Takahashi

et al. 2021

Aeronaut. j.

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With an annual growth in travel demand of about 5% globally, managing the environmental impact is a challenge. In 2019, the International Civil Aviation Organisation (ICAO) issued emission reduction targets, including well-to-wake greenhouse gas (GHG) emissions reduced at least 50% from 2005 levels by 2050. This discusses several technologies from an aircraft design perspective that can contribute to achieving these targets. One thing is certain: aircraft will look different in the future. The Transonic Truss-Braced Wing and Flying V configurations are promising significant efficiency improvements over conventional configurations. Electric propulsion, in various architectures, is becoming a feasible option for general aviation and commuter aircraft. It will be a growing field of aviation with zero-emissions flight and opportunities for special missions. Lastly, this paper discusses methods and design processes that include all relevant disciplines to ensure that the aircraft is optimised as a complete system. While empirical methods are essential for initial design, Multidisciplinary Design Optimisation (MDO) incorporates models and simulations integrated in an optimisation environment to capture critical trade-offs. Concurrent design places domain experts in one site to facilitate collaboration, interaction, and joint decision-making, and to ensure all disciplines are equally considered. It is supported by a Collaborative Design Facility (CDF), an information technology facility with connected hardware and software tools for design analysis.

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Development of an Efficient M=0.80 Transonic Truss-Braced Wing Aircraft

Cited by 24 publications

References 0 publications

Fuel burn evaluation of a transonic strut-braced-wing regional aircraft through multipoint aerodynamic optimisation

Fuel burn evaluation of a transonic strut-braced-wing regional aircraft through multipoint aerodynamic optimisation

Structural Power Performance Targets for Future Electric Aircraft

Future aircraft concepts and design methods

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